EP3969743A1 - Pale de rotor et éolienne - Google Patents

Pale de rotor et éolienne

Info

Publication number
EP3969743A1
EP3969743A1 EP20727212.1A EP20727212A EP3969743A1 EP 3969743 A1 EP3969743 A1 EP 3969743A1 EP 20727212 A EP20727212 A EP 20727212A EP 3969743 A1 EP3969743 A1 EP 3969743A1
Authority
EP
European Patent Office
Prior art keywords
rotor blade
gurney flap
thickness
length
height
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP20727212.1A
Other languages
German (de)
English (en)
Inventor
Hauke Maass
Jochen STEMBERG
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Wobben Properties GmbH
Original Assignee
Wobben Properties GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Wobben Properties GmbH filed Critical Wobben Properties GmbH
Publication of EP3969743A1 publication Critical patent/EP3969743A1/fr
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/065—Rotors characterised by their construction elements
    • F03D1/0675—Rotors characterised by their construction elements of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/0608—Rotors characterised by their aerodynamic shape
    • F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
    • F03D1/0641—Rotors characterised by their aerodynamic shape of the blades of the section profile of the blades, i.e. aerofoil profile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/50—Building or constructing in particular ways
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/305—Flaps, slats or spoilers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/70—Shape
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Definitions

  • the invention relates to a rotor blade of a wind energy installation with a Gurney Flap, an associated wind energy installation and an associated method.
  • Wind energy plants are known in principle. Modern wind energy systems generally relate to so-called horizontal-axis wind energy systems, in which the rotor axis is arranged essentially horizontally and the rotor blades sweep over an essentially vertical rotor surface.
  • wind energy installations generally comprise a tower on which the nacelle with the rotor is arranged such that it can rotate about an essentially vertically aligned axis.
  • the rotor usually comprises one, two or more rotor blades of the same length.
  • the rotor blades are slim components that are often made of fiber-reinforced plastic.
  • a rotor blade In an area adjacent to the rotor blade flange, a rotor blade generally has a circular cylinder geometry.
  • the circular cylinder geometry is usually necessary to implement pitch-regulated rotor blades.
  • Pitch-regulated rotor blades are rotatably mounted on the hub or in another position in order to move them in a rotary manner at least partially about their longitudinal axis.
  • this object is achieved by a rotor blade for a wind turbine with a rotor blade length, a rotor blade depth extending over the rotor blade length, a rotor blade thickness extending over the rotor blade length and a rear edge thickness of the rotor blade extending over the rotor blade length, comprising a Gurney Flap with an over the height of the rotor blade length, the height of the Gurney Flap depending on the thickness of the trailing edge is dimensioned in such a way that a ratio of the height of the Gurney Flap and the thickness of the trailing edge is between greater than 0% and 25%, in particular between 5% and 25% , is.
  • the invention is based on the knowledge that Gurney flaps with such a restricted height lead to a surprisingly positive influence on the flow. It is also a finding of the present invention that the ratio of the height of the Gurney Flap and the thickness of the trailing edge can be used with particular advantage for aerodynamic optimization of a rotor blade, in particular an area of a rotor blade close to the hub.
  • the inventors of the present invention have found in particular that the most effective possible increase in lift in the area near the hub depends in a particular way on the ratio of the height of the Gurney Flap and the thickness of the trailing edge.
  • the rotor blade extends with a rotor blade length, a rotor blade depth and a rotor blade thickness.
  • the rotor blade length is defined in particular as the distance between a rotor blade flange and a rotor blade tip, between which the rotor blade extends.
  • the rotor blade depth is in particular aligned essentially orthogonally to the rotor blade length. In operation, the rotor blade depth is aligned essentially parallel to the direction of flow towards the rotor blade.
  • the rotor blade depth preferably extends between a leading edge and the trailing edge of the rotor blade.
  • the rotor blade extends orthogonally to the rotor blade length and the rotor blade depth in the direction of the rotor blade thickness.
  • the rotor blade depth and the rotor blade thickness span an aerodynamic profile, which can also be understood as a profile section, at essentially every position along the rotor blade length. In an area of the rotor blade near the hub, this can have a fiatback profile, which is defined in more detail below.
  • a Fiatback profile is characterized in particular by the fact that it does not have a closed, tapering rear edge profile.
  • the Fiatback profile deviates from the essentially teardrop-shaped shape and has an essentially angular rear edge geometry.
  • the direction of the thickness of the trailing edge is oriented essentially parallel to the rotor blade thickness and orthogonally to the rotor blade length and orthogonally to the rotor blade depth.
  • a thickness of the rear edge of the rotor blade can, however, also be defined for profiles that have rounded corners or also closed profiles, in particular in the form of drops.
  • the thickness of the rear edge is understood to mean, in particular, the distance between the profile pressure side contour and the profile suction side contour at the root point of the Gurney Flap orthogonal to the profile chord of the rotor blade.
  • Structural framework conditions for example the layer structure or the ability to be demolded from a mold, may make it necessary to have the rear edge of the rotor blade in a rounded shape on both the pressure side and the suction side. In this case it is advantageous to position the Gurney Flap in an area in front of the actual flat trailing edge of the profile.
  • the aforementioned profile pressure side contour and profile suction side contour preferably ends before the rounding. The rounding is thus in particular not part of the profile pressure side contour and the profile suction side contour, so that the thickness of the rear edge is determined before the actual flat rear edge.
  • the rotor blade also has the Gurney Flap.
  • a Gurney Flap is in particular an edge that protrudes from the rotor blade surface.
  • a Gurney Flap usually has the effect that the flow at the trailing edge of the rotor blade is influenced, preferably in such a way that a pressure increase occurs in front of the Gurney Flap and a pressure drop behind the Gurney Flap.
  • the Gurney Flap causes an increase in circulation, the outflow angle, defined as the angle between the profile chord and the direction of the outflow, and the deflection angle, defined as the angle between the direction of the inflow and the outflow, being increased.
  • the peeling area is usually Relocated behind the Gurney Flap. As a result, the lift on the rotor blade and the drag are increased.
  • the Gurney Flap protrudes from a rotor blade surface.
  • the height of the Gurney Flap is to be understood in particular as a cantilever height.
  • the height of the Gurney Flap is specifically defined as the distance between a root point and a tip point of the Gurney Flap.
  • the root point of the Gurney Flap is in particular the point at which the Gurney Flap meets the rotor blade.
  • the tip point of the Gurney Flap is to be understood in particular as the distal end of the Gurney Flap. This height can vary along the length of the rotor blade.
  • the height of the Gurney Flap is therefore preferably not a constant value, but rather variable as a function of the rotor blade length.
  • a ratio of the height of the Gurney Flap and the thickness of the trailing edge can be determined for each profile section.
  • the value of the ratio of the height of the Gurney Flap and the thickness of the rear edge results from dividing the height of the Gurney Flap by the thickness of the rear edge.
  • the ratio of the height of the Gurney Flap and the thickness of the rear edge is between greater than 0% and 25%. In particular, it is preferred that the ratio of the height of the Gurney Flap and the thickness of the rear edge is between 5% and 25%.
  • the ratio of the height of the Gurney Flap and the thickness of the rear edge is greater than 5%, greater than 7.5%, greater than 10% or greater than 15%.
  • Such an unusually high ratio of the height of the Gurney Flap and the thickness of the trailing edge results in a surprisingly high lift of the rotor blade.
  • the ratio of the height of the Gurney Flap and the thickness of the rear edge is greater than 5%, greater than 7.5%, greater than 10% or greater than 15% in an area close to the hub, in particular between 0% and 50%, preferably between 3% and 35% of the relative sheet length.
  • the ratio of the height of the Gurney Flap and the thickness of the trailing edge is between greater than 0% and 25% in a rotor blade area near the hub.
  • the rotor blade area near the hub is preferably characterized in that it extends from greater than or equal to 0% to a maximum of 35% of the relative blade length.
  • the relative blade length is preferably defined in such a way that it ranges from 0% to 100%, with 0% characterizing an end facing the hub, for example the rotor blade flange, and 100% characterizing the blade tip. With a relative blade length of greater than 35%, in particular greater than 50%, the ratio of the height of the Gurney Flap and the thickness of the rear edge preferably approaches zero. In particular, this can be the case towards the blade tip.
  • An advantageous development of the rotor blade is characterized in that the ratio of the height of the Gurney Flap and the thickness of the trailing edge increases to a maximum value starting from a rotor blade flange or starting from an area adjacent to the rotor blade flange.
  • the height of the Gurney Flap is preferably dimensioned along the length of the rotor blade in such a way that the ratio of the height of the Gurney Flap and the thickness of the trailing edge towards the blade tip initially increases.
  • the Gurney Flap preferably extends from an inner end to an outer end, the inner end facing the rotor blade flange and the outer end facing the rotor blade tip. Starting from the inner end, the ratio of the height of the Gurney Flap to the thickness of the rear edge increases to a maximum of this ratio. Starting from this maximum towards the outer end of the Gurney Flap, the ratio of the height of the Gurney Flap to the thickness of the rear edge preferably decreases again. The maximum of the ratio can also occur at the outer end of the Gurney Flap.
  • the ratio can increase directly starting from the rotor blade flange or starting from an area adjacent to the rotor blade flange. This means in particular that the Gurney Flap does not necessarily begin directly on the rotor blade flange, but can also begin at a distance from the rotor blade flange. This spacing can be, for example, 3% of the rotor blade length.
  • the maximum value of the ratio between the height of the Gurney Flap and the thickness of the trailing edge is between 5% and 15%, preferably between 6% and 12%, of the relative blade length.
  • the maximum value of this ratio is preferably reached between 5% and 15% of the relative sheet length. In the case of a rotor blade with a rotor blade length of 80 meters, for example, this means that the maximum value of the ratio of the height of the Gurney Flap and the thickness of the trailing edge is reached between 4 meters and 12 meters from the rotor blade flange. In particular, it is preferred that this maximum value of the ratio is 4.8 meters to 8.8 meters from the rotor blade flange.
  • the Gurney Flap is arranged between 3% and 35% of the relative blade length on the rotor blade.
  • the inner end of the Gurney Flap is spaced apart from the rotor blade flange.
  • the inner end of the Gurney Flap can for example be arranged at 3% of the relative leaf length.
  • the inner end of the Gurney Flap can also be spaced apart from the rotor blade flange by more than 3% of the relative blade length.
  • the outer end of the Gurney Flap can be located at 35% of the relative leaf length. It is also preferred that the outer end of the Gurney Flap is arranged at 50%, or less than 50%, in particular at less than 35% of the relative leaf length, for example at 30%.
  • the Gurney Flap preferably extends from the inner end to the outer end with a Gurney Flap length.
  • Gurney Flap length is preferably between greater than 0% and 50%, more preferably between greater than 0% and 30%, further preferably between 10% and 25% of the relative leaf length. It is further preferred that the Gurney Flap length is less than or equal to 50% of the relative leaf length.
  • Another preferred development of the rotor blade is characterized in that the Gurney Flap is arranged on a pressure side of the rotor blade.
  • Rotor blades usually have a pressure side and a suction side.
  • the pressure side is in particular the side of the rotor blade on which the flow velocity is low and the pressure is high compared to the suction side.
  • an angle between the height of the Gurney Flap and a chord of the rotor blade is between 90 ° and 170 °, in particular at least 100 °, preferably at least 1 10 °.
  • the profile chord is preferably defined in the profile section in such a way that it is the connecting line between the center point of the rear edge and the front edge.
  • the center of the rear edge is preferably the point on the rear edge which is at the same distance from the pressure side and from the suction side.
  • the front edge is understood to mean, in particular, the point of the profile outer contour which is the maximum distance from the center point of the rear edge.
  • a ratio of the height of the Gurney Flap and the rotor blade depth at a profile section of the rotor blade length is more than 1%, more than 2% and / or more than 5%.
  • a ratio of the height of the Gurney Flap and the rotor blade depth is more than 1%, more than 2% and / or more than 5%.
  • a ratio of the height of the Gurney Flap and the rotor blade depth is more than 10% and / or more than 15% % is.
  • a ratio of the height of the Gurney Flap and the rotor blade depth between 1% and 20%, preferably between 2% and 15%, in particular between 5% and 15%.
  • the ratio of the height of the Gurney Flap and the thickness of the trailing edge is in a range between 0% and 5% of the relative blade length between 4% and 25%, in particular between 10% and 21% , is; and / or in a range between 5% and 10% of the relative sheet length between 4% and 25%, in particular between 12% and 22%; and / or in a range between 10% and 15% of the relative sheet length between 0% and 25%, in particular between 13% and 20%; and / or in a range between 15% and 20% of the relative sheet length between 0% and 23%, in particular between 10% and 18%; and / or in a range between 20% and 25% of the relative sheet length between 0% and 20%, in particular between 0% and 15%; and / or in a range between 25% and 30% of the relative sheet length between 0% and 15%, in particular between 0% and 10%; and / or in a range between 30% and 35% of the relative sheet length between 0% and 10%.
  • the ratio of the height of the Gurney Flap and the thickness of the rear edge is thus preferably between 4% and 25%.
  • the Gurney Flap can, for example, have an inner end at 3% of the relative leaf length and have a height such that a ratio of the height of the Gurney Flap and the thickness of the rear edge is 10%.
  • the range specifications for the ratio of the height of the Gurney Flap and the thickness of the rear edge apply to each profile section in the specified range of the relative blade length.
  • the specified values for the ratio of the height of the Gurney Flap and the thickness of the rear edge are specific individual values at a defined position in the specified area, i.e. preferably for a profile section.
  • the ratio of the height of the Gurney Flap and the thickness of the rear edge is preferably determined by means of a quadratic function.
  • the ratio of the height of the Gurney Flap and the thickness of the rear edge lies in a design range, the design range being defined by an upper limit value curve fmax and by a lower limit value curve fmin.
  • the limit value curves are preferably determined by a function of the following form:
  • r / R represents the relative radius position; it is the relative radius position taking into account the rotor blade hub.
  • the reference length is therefore the entire rotor radius taking into account the rotor blade hub and the rotor blade length r is, for example, the distance between the position under consideration in meters from the axis of rotation of the rotor and R is the sum of the rotor blade length and distance from the blade flange to the axis of rotation.
  • z / Z represents the relative blade length in the above-mentioned context. z is, for example, the distance between the considered position in meters from the blade flange and Z is the rotor blade length.
  • the value a has a minimum value of -5, or -4, or -3, or -2.5. It is also preferred that the value a has a maximum value of -2.5, or -2, or -1, or 0 for the upper limit value curve fmax.
  • the value b has a minimum value of -1, or 0, or 0.3. Furthermore, it is preferred that for the upper limit value curve
  • Limit value curve fmax the value b has a maximum value of 0.2, or 0.3, or 0.5, or 1.
  • the value c has a minimum value of 0, or 0.1, or 0.2, or 0.3. It is also preferred that the value c has a maximum value of 0.2, or 0.3, or 0.4, or 1 for the upper limit value curve.
  • the value a has a minimum value of -10, or -8, or -5, or -3. It is also preferred that the value a has a maximum value of -5, or -4, or -3, or 0 for the lower limit value curve fmin.
  • the value b has a minimum value of 0, or 0.3, or 0.5. Furthermore, it is preferred that the value b has a maximum value of 0.3, or 0.5, or 0.6, or 1 for the lower limit value curve fmin.
  • the value c has a minimum value of 0, or 0.01, or 0.02, or 0.03, or 0.04, or 0.05. It is further preferred that the value c for the lower limit value curve fmin has a maximum value of 0.02, or 0.03, or 0.04, or 0.1.
  • the rotor blade has a Fiatback profile with or without rounded edge areas and the thickness of the flinter edge is defined as the distance between a profile contour of the pressure side and a profile contour of the suction side orthogonal to the profile chord.
  • the rounded edges are preferably not part of the profile contour of the pressure side and / or the suction side.
  • the Gurney Flap is preferably arranged at the transition from the profile contour of the pressure side to the rounded edge area.
  • the Gurney Flap can also be arranged from this position towards the profile contour of the pressure side or also into the rounded edge area.
  • the rotor blade has a closed profile and the thickness of the flinter edge as the distance between a profile contour of the pressure side and a profile contour of the suction side orthogonal to the profile chord at the point of Rotor blade depth is defined at which a free pressure side flow prevails during operation, this point preferably being defined by the root point of the Gurney Flap.
  • a closed profile is to be understood as the usual, in principle, essentially teardrop-shaped geometry of a rotor blade cross section.
  • a closed profile is understood to mean a profile which has a tapering rear edge and therefore no significant thickness of the rear edge can be determined directly at the rear edge.
  • the thickness of the trailing edge is understood as the distance between the profile contour of the pressure side and the profile contour of the suction side orthogonal to the profile chord at the point of the rotor blade depth at which a free pressure side flow prevails during operation.
  • the free pressure side flow prevails in the relevant operating range in particular up to the point at which a pressure side flow separation occurs and at which a Gurney Flap is preferably arranged.
  • a relevant operating range is defined, for example, from the partial load range at an optimal high speed up to reaching the rated power.
  • the thickness of the rear edge can be understood as the distance between the profile contour of the pressure side and the profile contour of the suction side orthogonal to the profile chord at the point of the rotor blade depth at which the Gurney Flap is arranged.
  • a pressure side detachment occurs in profile sections with high relative thicknesses at the point where a complete flow around the rotor blade on the pressure side is no longer guaranteed.
  • the rotor blade comprises a transition area, the transition area consisting of a section with a Fiatback profile and a section with a circular cylinder profile, the section with the circular cylinder profile facing the rotor blade flange, and the Gurney Flap being arranged in the transition area.
  • the transition area preferably comprises the rotor blade flange and / or a blade connection.
  • the circular cylinder profile of a rotor blade is characterized in particular by the fact that it has a lift coefficient of essentially zero. Consequently, it is particularly preferable in this area to arrange the Gurney Flap which improves the lift coefficient.
  • the thickness of the rear edge in the case of a circular cylinder profile is understood in particular to mean the diameter of the circular cylinder.
  • the Gurney Flap extends in the direction of height from a root point to a tip point, and / or the Gurney Flap has a thickness orthogonal to the direction of height that is essentially parallel to the chord of the profile Rotor blade is aligned, and / or the Gurney Flap extends orthogonally to the direction of the height and orthogonally to the thickness in a longitudinal direction, and preferably a flat extension is formed by the extension in the longitudinal direction and the height.
  • the thickness of the Gurney Flap is to be understood in particular as the material thickness of the material of the Gurney Flap.
  • the longitudinal direction of the Gurney Flap can be straight, curved or curved.
  • the rotor blade comprises a blade adapter and / or a blade extension, the blade adapter and / or the blade extension having or have the rotor blade flange.
  • the object mentioned at the beginning is achieved by a wind energy installation, comprising a rotor blade according to one of the embodiment variants explained above.
  • the object mentioned at the beginning is achieved by a wind park with at least two wind energy plants according to the previous aspect.
  • the aforementioned object is achieved by a method for designing a rotor blade of a wind turbine with a rotor blade length, a rotor blade depth extending over the rotor blade length, a rotor blade thickness extending over the rotor blade length and a rear edge of the rotor blade thickness extending over the rotor blade length, comprising a Gurney Flap with a height extending over the length of the rotor blade, the height of the Gurney Flap being dimensioned as a function of the thickness of the trailing edge such that a ratio of the height of the Gurney Flap and the thickness of the trailing edge is between greater than 0% and 25%, in particular between 5% and 25%.
  • the method and its possible further developments have features or method steps which make them particularly suitable for being used for the rotor blade according to the first aspect and its further developments.
  • design variants and design details of the further aspects and their possible further developments reference is also made to the description given above for the corresponding features and further developments of the rotor blade.
  • FIG. 1 a schematic, three-dimensional view of a wind energy installation
  • Figure 2 a schematic, three-dimensional view of an embodiment of a
  • FIGS. 3-5 top views of the rotor blade shown in FIG. 2;
  • FIG. 6 a schematic, two-dimensional view of another
  • FIG. 7 a schematic, two-dimensional view of a rotor blade with a Fiatback profile
  • FIG. 8 a schematic, two-dimensional view of a rotor blade with a closed profile
  • FIG. 9 a schematic view of a design area for the relationship between the height of the Gurney Flap and the thickness of the rear edge.
  • FIG. 1 shows a schematic, three-dimensional view of a wind energy installation 100.
  • the wind energy installation 100 has a tower 102 and a gondola 104 on the tower 102.
  • An aerodynamic rotor 106 with three rotor blades 108, each of which has a rotor blade length R, and a spinner 110 are provided on the nacelle 104.
  • the aerodynamic rotor 106 is driven by the wind when the wind power installation 100 is in operation set in a rotary motion and thus also rotates an electrodynamic rotor or rotor of a generator, which is coupled directly or indirectly to the aerodynamic rotor 106.
  • the electrical generator is arranged in the nacelle 104 and generates electrical energy.
  • the pitch angles of the rotor blades 108 can be adjusted by pitch motors to the
  • the rotor blades 108 have a rear edge thickness extending over the rotor blade length R.
  • the rotor blades 108 also have Gurney flaps, which cannot be seen here, with a height extending over the rotor blade length R.
  • the height of the Gurney Flaps is dimensioned as a function of the thickness of the rear edges, specifically such that a ratio of the height of the Gurney Flaps and the thickness of the rear edge is between greater than 0% and 25%, in particular between 5% and 25%.
  • FIGS. 2 to 5 show schematic, three-dimensional views of a further embodiment of a rotor blade 200.
  • the rotor blade 200 extends in the longitudinal direction L from a rotor blade flange 204 to a not shown
  • Rotor blade tip The rotor blade extends orthogonally to the longitudinal direction L with a rotor blade depth T and orthogonally to the rotor blade length L and orthogonally to the rotor blade depth T with a rotor blade thickness D.
  • the rotor blade 200 In an area adjoining the rotor blade flange 204, the rotor blade 200 has a circular cylinder profile 210. On a side of the circular cylinder profile 210 facing away from the rotor blade flange 204, the rotor blade 200 has a Fiatback profile 212. In a transition area, which consists of a section with the circular cylinder profile 210 and a section with the Fiatback profile 212, the rotor blade 200 has a Gurney flap 214.
  • the Gurney Flap 214 is arranged on the pressure side 206 of the rotor blade 200. In particular, the Gurney Flap 214 is arranged adjacent to a trailing edge 202 of the rotor blade 200.
  • FIG. 6 shows a schematic, two-dimensional view of a further embodiment of a rotor blade 300 with a fiatback profile.
  • the rotor blade 300 extends at the rotor blade depth T from a leading edge 302 to a trailing edge 304.
  • the rotor blade 300 is geometrically described, inter alia, by a chord 322.
  • the chord 322 is defined as the connecting line between the midpoint of the trailing edge 304 and the point 324 of the leading edge 302 which is the maximum distance from the midpoint of the trailing edge 304.
  • the profile has a rounded geometry.
  • the profile has a straight surface.
  • the rear edge can alternatively also have two or more surfaces which are arranged at an angle to one another.
  • the rear edge can have two surfaces which form an angle with one another, one of these surfaces forming an angle with the pressure side and the other surface forming an angle with the suction side. These angles form a sharp end edge on the pressure side and on the suction side in particular, at which the adjacent flow leaves the profile.
  • the rear edge can also be curved. Rear edges formed in this way can advantageously be removed from the mold. Such a profile is referred to as a fiatback profile because the trailing edge 304 is substantially flat. With a rear edge 304 configured in this way, the thickness 310 of the rear edge 304 can be determined directly by the spacing between the suction side 306 and the pressure side 308.
  • the Gurney Flap 312 is arranged at the transition from the pressure side 308 to the rear edge 304.
  • the Gurney flap 312 extends from a root point 314 to a tip point 316.
  • the root point 314 of the Gurney flap 312 is arranged on the rotor blade 300.
  • the tip point 316 of the Gurney Flap 312 is to be understood as a distal end of the Gurney Flap 312 and thus facing away from the rotor blade 300.
  • the Gurney Flap 312 has a height 318.
  • the height 318 is defined as the distance between the root point 314 and the tip point 316.
  • the arrangement of the Gurney Flap 312 is furthermore determined by an angle 320.
  • the angle 320 determined from the front edge 302, between the height 318 or the direction of the height 318 of the Gurney Flap 312 and the chord 322 can in particular be between 90 ° and 170 °. In the present exemplary embodiment, the angle 320 is approximately 100 °.
  • the rotor blade 300 'shown in FIG. 7 differs from the rotor blade shown in FIG. 6 by the profile geometry at the trailing edge 304'.
  • the profile geometry is characterized by rounded corners.
  • the thickness 310 of the trailing edge 304 ' is understood as the distance between the profile contour of the pressure side 308 and the profile contour of the suction side 306 orthogonal to the profile chord 322 at the point of the rotor blade depth T at which a free pressure side flow prevails during operation.
  • FIG. 8 shows a rotor blade 300 ′′ with a closed trailing edge 304 ′′.
  • the thickness 310 of the rear edge 304 ′′ is the distance between the profile contour of the pressure side 308 and the profile contour of the suction side 306 orthogonal to the profile chord 322 at the point of the rotor blade depth T at which a free pressure side flow prevails during operation.
  • FIG. 9 shows a schematic view of a design area for the ratio of the fleas 318 of the Gurney flap 312 and the thickness 310 of a rear edge 304, 304 ', 304 ".
  • the relative sheet length is plotted on the abscissa in a value range from 0% to 35%.
  • the ratio of the height 318 of the Gurney Flap 312 and the thickness 310 of the rear edge 304, 304 ', 304 ′′ is plotted on the ordinate in a value range between 0% and 30%.
  • the diagram shows a first design range 400 which is defined by a first upper limit line 402 and a first lower limit line 404.
  • r / R represents the relative radius position, it is the relative radius position taking into account the rotor blade hub.
  • the reference length is therefore the entire rotor radius taking into account the rotor blade hub and the rotor blade length r is, for example, the distance between the position under consideration in meters from the axis of rotation of the rotor and R is the sum of the rotor blade length and the distance from the blade flange to the axis of rotation.
  • z / Z represents the relative blade length in the above-mentioned context. z is, for example, the distance between the considered position in meters from the blade flange and Z is the rotor blade length.
  • the second design area 410 is arranged within the first design area 400.
  • the second design range is defined by the second upper limit value line 412 and the second lower limit value line 414.

Abstract

L'invention concerne une pale de rotor (108, 200, 300, 300', 300'') d'une éolienne, ladite pale de rotor étant dotée d'un volet de Gurney (214, 312), une éolienne associée et un procédé associé. L'invention concerne en particulier une pale de rotor (108, 200, 300, 300', 300'') pour une éolienne, présentant une longueur de pale de rotor (L), une profondeur de pale de rotor (T) s'étendant sur toute la longueur de pale de rotor (L), une épaisseur de pale de rotor (D) s'étendant sur toute la longueur de la pale de rotor (L) et une épaisseur (310) d'un bord de fuite (202, 304) de la pale de rotor (108, 200, 300, 300', 300''), s'étendant sur toute la longueur de la pale de rotor (L), ladite arête arrière comprenant un volet de Gurney (214, 312) ayant une hauteur (318) s'étendant sur toute la longueur de la pale de rotor (L), la hauteur (318) du volet de Gurney (214, 312) étant dimensionnée en fonction de l'épaisseur (310) du bord de fuite (202, 304), de sorte qu'un rapport entre la hauteur (318) du volet de Gurney (214, 312) et l'épaisseur (310) du bord de fuite (202, 304) se situe entre plus de 0 à 25%, en particulier entre 5 et 25%.
EP20727212.1A 2019-05-17 2020-05-15 Pale de rotor et éolienne Pending EP3969743A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019113085.9A DE102019113085A1 (de) 2019-05-17 2019-05-17 Rotorblatt und Windenergieanlage
PCT/EP2020/063713 WO2020234190A1 (fr) 2019-05-17 2020-05-15 Pale de rotor et éolienne

Publications (1)

Publication Number Publication Date
EP3969743A1 true EP3969743A1 (fr) 2022-03-23

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Application Number Title Priority Date Filing Date
EP20727212.1A Pending EP3969743A1 (fr) 2019-05-17 2020-05-15 Pale de rotor et éolienne

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US (1) US20220228551A1 (fr)
EP (1) EP3969743A1 (fr)
DE (1) DE102019113085A1 (fr)
WO (1) WO2020234190A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3981981A1 (fr) 2020-10-09 2022-04-13 Wobben Properties GmbH Pale de rotor pour une éolienne, éolienne et procédé de conception d'une pale de rotor

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265830A (en) * 1992-01-21 1993-11-30 Mcdonnell Douglas Corporation Trailing edge splitter
US7828523B2 (en) * 2007-03-27 2010-11-09 General Electric Company Rotor blade for a wind turbine having a variable dimension
DE102008026474A1 (de) * 2008-06-03 2009-12-10 Mickeler, Siegfried, Prof. Dr.-Ing. Rotorblatt für eine Windkraftanlage sowie Windkraftanlage
EP2138714A1 (fr) * 2008-12-12 2009-12-30 Lm Glasfiber A/S Pale d'éolienne dotée d'un dispositif de guidage d'écoulement de hauteur optimisée
DK177744B1 (en) * 2012-10-16 2014-05-19 Envision Energy Denmark Aps Wind turbine having external gluing flanges near flat back panel
GB2526847A (en) * 2014-06-05 2015-12-09 Vestas Wind Sys As Wind turbine blade with trailing edge flap
GB201417924D0 (en) * 2014-10-10 2014-11-26 Vestas Wind Sys As Wind turbine blade having a trailing edge flap
US10495056B2 (en) * 2015-09-03 2019-12-03 Siemens Gamesa Renewable Energy A/S Wind turbine blade with trailing edge tab
DE102015012427A1 (de) * 2015-09-25 2017-03-30 Senvion Gmbh Rotorblatt mit einem schalloptimierten Profil sowie Verfahren zum Herstellen eines Rotorblatts
DE202016101461U1 (de) * 2016-03-16 2016-03-31 Institute of Aerospace Technology (IAT) der Hochschule Bremen Rotorblatt für Windenergieanlagen mit horizontaler Drehachse sowieWindenergieanlage mit selbigem
DE102016117012A1 (de) * 2016-09-09 2018-03-15 Wobben Properties Gmbh Windenergieanlagen-Rotorblatt
GB2564884A (en) * 2017-07-26 2019-01-30 Vestas Wind Sys As Wind turbine blade with boundary layer fence

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DE102019113085A1 (de) 2020-11-19
US20220228551A1 (en) 2022-07-21
WO2020234190A1 (fr) 2020-11-26

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